Aerial machine.



F. T.- TAYLOR.

AERI AL MACHINE APPLIGATION PILED 00123 1909.

Patented Dec. 22, 1914.

supported. My device may also be em- FREIDEBICK WIIILIAM THOMAS TAYLOR, 01E CRIGKLEWOOD, LONDON, ENGLANI' nnnulr. MACHINE.

Specification of Letters Patent.

Application .filed October 23, 1909. Serial No. 5%,243.

To all whom it may concern Be it known that I, FREDERIC WILLIAM THOdIAS TAYLQR, of 7 Osborne road, Willes den Green, Cricklewood, London, N. W., England, have invented Improvements in or Connected with Aerial'Machines, of which the following is the specification;

This invention relates to means for carrying the method into effect by which an aerial machine may be wholly or partly lifted or ployed to effect better steering and to insure the stability of such machines. My invention in its simplest form consists of aplane of any suitable shapemounted on a spindle shaft, or pivots, in such a mention-that half of the area of the plane 'i'sflon one side ofsllch shaft or pivots and half on the other side. The vplaneis mounted to rotate freely with the said spindleor pivots, the said spindles or pivots being mounted in bearings fitted in a suitable frame or the like. The said plane is Dreferably a long and narrow rectangle, and the said pivots are fitted centrally in the ends of such rectangular plane. The center of gravity should coincide with the center of such shaft or spindle and therefore with the center of rotation.

In order that my invention may be completely understood, reference should bemade to the appended sheet of drawings.

Figure l is an endelevation of my apparatus shown fitted to an aeroplane having two planes. Fig. 2. is a plan ofthe same but with my rotating planes shown at right angles with the plane in,I*ig. 1. Fig. 3 is a-front elevation of the same with my rotary planes shown in the same position as in Fig. I. Fig. 4.- illustrates a detailed view of the clutches, which form connections between the* driven axle and the rotating planes. p g

A A A A are the rotating planes mounted on the spindle or shaft B and rotatable therewith. The shaft 18 maybe made as one continuous shaft, as shown, -or each plane A. may be mounted on a separate shaft. The shaft B is mounted in bearings which may be ball bearings carried by the pro-" jecting frame arms H of the aeroplane as shown, having the two planes C D of ordinary construction. The planes C D may be provided with a horizontal tail plane or planes, not shown, and with a vertical plane,

not shown, both of ordinary construction. the latter to eifect horizontal steering.

An engine is fitted to the frame of the aeroplane of anytype and any form of propeller may be employed for forward propul'sion.

The shaft B carries a sprocket wheel E" which is connected by chain G with a sprocket wheel F or the like directly in front of the-aeronaut. The sprocket Wheel F may be manually operated as by a crank handle of any appropriate type. This is not for the purpose of rotating the planes by power, but so that the planes or plane A may be started to rotate in the desired direction when the forward propulsion occurs.

The planes A have a decided lifting and supporting action when rotating in one direction, 2'. 6. with the leading edge ascending, and on the other hand a tendency to Patented Dec. 22, I914.

immediately plunge the aeroplane down,

ward if rotated in the opposite direction. Consequently, if the planes A A one the one side of the aeroplane are permitted to rotate at their full speed, and the planes on the other side are retarded or stopped, or rotated in the other direction, that side of the aeroplane with the retarded or stopped planes will tend to fall, while the other side will relatively rise. In this manner the stability of the aeroplane may be controlled as well as the horizontal steering action during which action it is necessary that the aeroplane shall be raised on the one side and correspondingl depressed on the other. The leading edge above referredto is the edgeof the plane which at any moment happens to be most advanced in he direction of flight. planes insure that the aeroplane cannot I plunge vertically to earth and it, or they,

by the plane in its line of flight, it follows that the speed of rotation is approximately proportional to the velocity of forward motion of the apparatus. In addition to the Moreover, the rota ing plane or Zldd lateral control efiected by differing speeds of the separated rotary. planes on the sides of the machine, the rotation of such planes produce great inherent lateral stability provided they are rotated together at uniform speed in the same direction. In addition to the longitudinal control ffected by checking orincreasing the speed of rotation ofthe leading'rotary plane, such rotary plane produces automatic longitudinal stability in association with any 'otherfollowing portionof the machine having amore constant lift. Owing to the high lifting efiiciency of the rotary plane (when rotated in the direction with the lea iing edge ascending), and

. mounted to slide on the driven axle B, and

to the variable and governable nature-of its lift as-herein described, the relation of the center of pressure to the center of gravity, in a machine eomprising such planes may be more easily-regulated and the efficiency of the whole machine, as well as its stability, be thereby increased.

The clutch members M and M are the teeth thereof are adapted to engage the stationary clutch members M and M l K and K are the brake shoes K and K which engage the eripheries of the rollers J and J for retar ing the movement of the planes after the clutches have been thrown out of operation. Itwill be clearly seen that the movement of the levers [K is effected only when the rods L and L, which have their ends terminating'at a point near the operators seat, have been moved. In order to assist in maintaining the rotation of the plane A, I have mounted the balance wheels Q adjacent the sprocket and on the stub axle E and E which are movable with the main axle B. This gearing, it will be noted, is supported within a frame formed of suitpipe or other tubular members shown at H.

As the direction of rotary spin of the plane or planes upon the apparatus deter' mines the direction in Which it is desired to move, therefore similar planes or vanes may be fitted placed vertical to the direction of flight, such similar planes may be employed mounted on vertical spindles for horizontal steering purposes.

ernor or a larger fly wheel may be used to govern the whole plane.

With the object of giving the planes the initial rotary movement and to maintain this rotation in the required dire'ction, they may be driven directly or indirectly by any suitable form of motor and the power may .be applied to retard or accelerate the rotary movement.

To further insure against a sudden reverse direction of rotation the shaft 13 of the planes may be provided with a suitable form of ratchet brake, serving to hold the plane until the application of the power causes it to resume its normal direction of revolution.

The dotted lines in Fig. 1 indicate how a similar plane may be mounted at the back of a biplane or other aeroplane toprovide the same lifting effect, or similar steering controL'at the back of the aeroplane as Well as at the front.

I claim z 1. In an aerial machine, superimposed main planes, and an auxiliary plane rotatably mounted on said main planes, and adapted to be actuated by the wind in one of two alternative directions, and means connectedwith'the auxiliary plane for starting the plane to rotate in the desired direction.

2. In an aerial machine, superimposed main planes, auxiliary planes supported by the main plane and adapted to be operated by the wind, and gearing associated with the auxiliary planes for starting the rotation of the planes in the desired direction.

3. In an aerial machine, main planes, auxiliary planes mounted to rotate in front of the main planes, an auxiliary rotatable plane mounted to operate at the rear of the main planes, said auxiliary planes being operated by the wind, and means for starting the auxiliary planes to rotate in predetermined directions.

FREDERICK WILLIAM THOMAS TAYLOR. I

Witnesses:

JAs. D. Roors, H. D. JAMEsoN. 

